Multifunctional valve and use of same in reaction control system

ABSTRACT

Various types of valves are disclosed, as well as the use of the same in a reaction control system for space travel vehicle applications. Multiple functions are provided by one of these valve designs by providing multiple flowpaths through the valve. An inflow and outflow tube of this multifunctional valve are fluidly interconnected with first and second chambers, respectively, within the valve. These first and second chambers are isolated from each other by a barrier assembly which may be “removed” at the desired type by a barrier rupture assembly to provide one of the noted multiple flowpaths (i.e., the inflow tube, the first chamber, the second chamber, and the outflow tube). A separate service port is fluidly interconnected with each of the first and second chambers, and a separate service valve may be disposed in each of these service ports to provide additional flowpaths for the multifunctional valve. One flowpath which exists prior to a rupturing of the barrier assembly includes the inflow tube, first chamber, and its associated service valve. Another flowpath which exists prior to a rupturing of the barrier assembly includes the outflow tube, second chamber, and its associated service valve. Another valve disclosed herein is a service valve for providing for a flow/no flow condition within a fluid system. This service valve includes a valve body and a valve stem which is slidably disposed within a bore within the valve body. The valve stem may be moved between at least two positions to terminate flow through within the valve body and to allow flow through the valve body, respectively. The service valve is configured so as to be resistant to side loads and provides redundant seals on redundant sealing surfaces. In this regard, the service valve includes at least three longitudinally-spaced radial seals between the valve body and valve stem, which are appropriately sized and oriented relative to each other to provide the desired functions.

CROSS-REFERENCE TO RELATED APPLICATIONS

This patent application claims priority from U.S. Provisional PatentApplication No. 60/134,707, filed May 18, 1999, and entitled “ReactionControl System Service Valve,” the entire disclosure of which isincorporated by reference in its entirety herein, as well as U.S.Provisional Patent Application No. 60/134,765, filed May 18, 1999, andentitled “Multifunctional Reaction Control System Valve,” the entiredisclosure of which is incorporated by reference in its entirety herein.

STATEMENTS REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT

Not applicable.

FIELD OF THE INVENTION

The present invention generally relates to systems through which a fluidflow may be directed and, more particularly, to a service valve whichmay be utilized in such system to provide both “flow through” and “noflow” conditions in relation to the service valve.

BACKGROUND OF THE INVENTION

Fluids are transferred in various types of systems and to providevarious types of functions. Reaction control systems are used by launchvehicles and in other spacecraft/spacecraft applications as well.Various types of fluids are transferred within these types of systems toprovide various types of functions. Components of one known prior artreaction control system include a ullage bottle which is disposed withina rigid rocket fuel storage bottle. The ullage bottle is fluidlyinterconnectable with a pneumatics system by a first fluid conduit whichincludes a first pyrotechnic isolation valve. A first service valveinterfaces with this first fluid conduit at a location which is betweenthe first pyrotechnic isolation valve and the ullage bottle to allow anappropriate fluid (e.g., helium) to be directed into and removed fromthe ullage bottle prior to activating the first pyrotechnic isolationvalve and for purposes which are addressed below.

A second fluid conduit interconnects the rocket fuel storage bottle witha rocket fuel tank. One or more rocket engine modules in turn arefluidly interconnected with this rocket fuel tank. Therefore, thestorage bottle is a “holding tank” of sorts for the rocket fuel. Asecond pyrotechnic isolation valve is disposed within the second fluidconduit to isolate the storage bottle from the rocket fuel tank untilthe desired time. A second service valve interfaces with the secondfluid conduit at a location which is between the second pyrotechnicisolation valve and the rocket fuel storage bottle to allow anappropriate rocket fuel (e.g., hydrazine) to be loaded within andunloaded from the storage bottle prior to activation of the secondpyrotechnic isolation valve and using the above-noted first servicevalve. More specifically, fluid may be directed into the ullage bottlethrough the first service valve to unload rocket fuel from the storagebottle and without providing the same to the rocket fuel tank. Fluidwhich is directed into the ullage bottle expands the same, which in turnforces rocket fuel out of the rocket fuel storage bottle and through thesecond service valve. A vacuum may be drawn through the first servicevalve as well to facilitate the loading of fuel within the rocket fuelstorage bottle by directing the rocket fuel through the second servicevalve and into the storage bottle prior to an activation of the secondpyrotechnic isolation valve, and thereby without directing any of suchrocket fuel into the rocket fuel tank.

A third service valve of the noted prior art reaction control systeminterfaces with the second fluid conduit at a location which is betweenthe second pyrotechnic isolation valve and the rocket fuel tank to allowa gas to be introduced into and removed from the rocket fuel tank and/orrocket engine modules interconnected therewith prior to activation ofthe second pyrotechnic isolation valve. For instance, it may bedesirable to introduce an appropriate gas (e.g., nitrogen) into therocket fuel tank and within the rocket engine modules to retain the samein a “clean” condition until a certain amount of time before the rocketengine modules are to be activated. At the appropriate time, this gasmay be removed from the rocket fuel tank and rocket engine modulesthrough the third service valve by drawing a vacuum through the same.Thereafter and at the appropriate time, the first and second fluidisolation valves may be simultaneously activated to remove the isolationbetween the ullage bottle and the pneumatics system and between therocket fuel storage bottle and the rocket fuel tank. Fluid which isdirected into the ullage bottle by the pneumatics system expands thesame. Reduction of the inner volume of the storage bottle forces rocketfuel out of the same and through the second pyrotechnic isolation valveto the rocket fuel tank for use by the rocket engine modules.

The above-noted prior art system has the noted isolation and servicevalves each being separately interconnected with the reaction controlsystem by welds or the like. Moreover, each of these service valves andpyrotechnic isolation valves are mounted on separate panels in thisprior art system. The disadvantages of this particular systemconfiguration and assembly technique include that it is much more costlyand labor intensive to install.

The service valves utilized by the above-noted prior art reactioncontrol system open and close the flow of fluids, such as liquids andgases, from one tank to another tank. Valves generally of this type arecurrently available from Moog and OEA, Inc., and utilize ametal-to-metal seal (e.g., metal ball against a metal channel) to closeor seal the valve. In such cases, to avoid leakage, the metal ball andmetal channel must be made with a high degree of precision to ensure anadequate seal is achieved. In addition, such metal-to-metal seals insuch existing service valves require a specific torque to seal the valve(e.g., 45 inch pounds, plus or minus 2 inch pounds). Otherwise, the sealformed by the metal ball and metal channel may leak, which isparticularly dangerous in instances where the fluid is a hypergolicfluid, such as hydrozene. For example, in instances where themetal-to-metal seal is under-torqued, leakage may occur. In otherinstances, where the metal-to-metal is over-torqued, the metal ball maybe galled, which may also cause leakage. And since such valves aretypically hand-tightened, the amount of torquing of the valves isgenerally inconsistent, and is often under-torqued or over-torqued. Whensuch metal-to-metal seals leak, in order to replace such valves, thevalves must be typically be cut-out since such valves are againtypically welded in place. In addition, the normal flow area in suchcurrently available valves is small, and, as such, filling a tank with afluid through such currently existing valves requires a great deal oftime. In instances where the fluid is a hypergolic fluid, due to thepoisonous and explosive nature of the fluid, the area must be evacuatedfor an extended period of time during the flow of fluid through thevalve. Finally, such existing valves require a series of brackets tosupport the valve since such valves are subject to side loading. Suchside loading can adversely affect the seal by gallings side surfaces ofthe valve, which may also cause leakage.

BRIEF SUMMARY OF THE INVENTION

Certain aspects of the present invention relate to a multifunctionalvalve. Other aspects of the present invention relate to a fluid transfersystem, such as reaction control system for a launch vehicle or otherspacecraft application, which includes at least one of the notedmultifunctional valves and at least one service valve to control theflow of fluid throughout this system in a desired manner. Still otheraspects of the present invention relate to a particular service valvedesign, and which is preferably utilized by the above-noted fluidtransfer system.

By way of initial summary, one general aspect of the present inventionrelates to a multifunctional valve which is designed to be used inlaunch vehicle or spacecraft reaction control systems. Generally, thismultifunctional valve is an integrated component, and is particularlyuseful in reaction control systems for launch vehicles and/or spacecraftsince this particular multifunctional valve combines all of the requiredelements of previous reaction control systems. Specifically, a firstsuch multifunctional valve may be utilized upstream of a fuel storagecontainer to provide for fuel container pressurization, and a secondsuch multifunctional valve may be utilized downstream of the fuelstorage container to provide for fuel container loading and unloadingand to provide for reaction control system loop blanket pressuremaintenance. By virtue of utilizing first and second suchmultifunctional valves in a reaction control system for launch vehicleor spacecraft applications, interconnecting welds between systemcomponents is eliminated, and prior practices of assembling allcomponents on panels and connecting such components with tubes is nolonger required. As such, the particular multifunctional valves providefor a more compact reaction control system than panel assembledcomponents, weighs less than the assembly of panel components, and isless expensive than such existing panel assemblies. Furthermore,utilization of these particular multifunctional valves in such reactioncontrol systems provides for a more flexible and versatile assembly.

Continuing with the initial summary, another general aspect of thepresent invention again relates to a service valve. Preferably thisparticular service valve has an increased fluid or gas flow rate and animproved sealing capability which is not dependent upon a specificapplied torque to seal the valve. One object of this service valvedesign is thereby that the same does not require torque to seal thesame. It is another object of this service valve design is thereby tohave an increased flow-throughput. It is yet another object of thisservice valve design to thereby be capable of withstanding shear loadswithout utilization of a series of brackets. It is a further object thisservice valve design to thereby have redundant sealing capabilities.

The above-noted general aspects of the present invention will now beaddressed in greater detail.

A first aspect of the present invention is generally directed to a fluidtransfer system or a system through which fluids may be transferred. Thefirst aspect includes first and second fluid system components (e.g.,fuel storage vessels or tanks) and a first fluid conduit which fluidlyinterconnects these first and second fluid system components. A valveassembly is disposed somewhere within the first fluid conduit andincludes a valve body. An inlet and outlet extend within this valve bodyfor directing fluid within, out of, and/or through the valve body, suchthat the inlet and outlet establish fluid communication between thevalve body and the corresponding portion of the first fluid conduit. Afirst chamber is disposed within the valve body and is fluidlyinterconnected with the inlet, while a second chamber is disposed withinthe valve body and is fluidly interconnected with the outlet. Isolationof the first chamber from the second chamber within the valve body, andthereby also the inlet and outlet, until a certain time is provided by abarrier assembly. Prior to a removal of this isolation by a barrierrupture assembly, it may be desirable to utilize the valve assembly todirect a flow through a flowpath which includes the first chamber,inlet, and a portion of the first fluid conduit fluidly interconnectedtherewith, through a flow path which includes the second chamber,outlet, and a portion of the first fluid conduit fluidly interconnectedtherewith, or both. In this regard, the valve assembly of the subjectfirst aspect also includes a first service port which extends within thevalve body, which is fluidly interconnected with the first chamber bothprior to and after any rupturing up the barrier assembly, and whichreceives a first service valve therein. Similarly, the valve assemblyalso includes a second service port which extends within the valve body,which is fluidly interconnected with the second chamber both prior toand after any rupturing up the barrier assembly, and which receives asecond service valve therein.

The valve assembly of the subject first aspect of the present inventionis multifunctional by providing multiple flowpaths. Initially and priorto a rupturing of the barrier assembly, the valve assembly serves toisolate that part of the first fluid conduit which interfaces with theinlet of the valve body from that part of the first fluid conduit whichinterfaces with the outlet of the valve body, and thereby serves toisolate the first fluid system component from the second fluid systemcomponent. Another function provided by the valve assembly associatedwith the first aspect and prior to a rupturing of the barrier assemblyis that a flow may be directed through the first service valve, withinthe first chamber, through the inlet, and through that portion of thefirst fluid conduit which interfaces with this inlet, and vice versa.Similarly, prior to a rupturing of the barrier assembly a flow may bedirected through the second service valve, within the second chamber,through the outlet, and through that portion of the first fluid conduitwhich interfaces with this outlet, and vice versa. Yet another functionwhich made provided by the valve assembly associated with the firstaspect of the present invention that it may serve to allow a flowbetween the first and second fluid system components after the barrierassembly is appropriately ruptured by the barrier rupture assembly. Sucha flow would thereby be through the valve assembly after the isolationbetween its first and second chambers, and thereby between its inlet andoutlet, is removed.

Various refinements exist of the features noted in relation to the firstaspect of the present invention. Further features may also beincorporated in the first aspect of the present invention as well. Theserefinements and additional features may exist individually or in anycombination. At least one pressure transducer may be interconnected withthe valve body and fluidly interface with the first or second chambersprior to a rupturing of the barrier assembly. One pressure transducercould be provided so as to directly fluidly interface with either thefirst chamber or the second chamber. Prior to a rupturing of the barrierassembly, this particular pressure transducer would then monitor thepressure only within the first or the second chamber. After a rupturingof the barrier assembly, this particular pressure transducer would thenmonitor the pressure of the fluid traveling through the valve assembly.One pressure transducer could be provided for the first chamber andanother pressure transducer could be provided for the second chamber aswell such that the pressure in both of these chambers could be monitoredboth before a rupturing of the barrier assembly and after a rupturing ofthe barrier assembly.

The barrier assembly of the first aspect of the present invention mayinclude at least one partition. This partition(s) may be integrallyformed with the valve body. A pair of partitions may be utilized as welland may be spaced within the valve body. In this regard, the barrierrupture assembly would also then preferably include an initiator and acorresponding projectile for the first of these partitions, and aseparate initiator and corresponding projectile for the second of thesepartitions. Rupturing either the first and/or second partition willfluidly interconnect the first and second chambers within the valvebody, such that the use of multiple partitions and multiple barrierrupture subassemblies may be characterized as being for purposes ofproviding redundancy.

One particular application for the fluid transfer system of the subjectfirst aspect is for space travel vehicles and the like. In oneembodiment, the first and second fluid system components are eachstorage vessels or tanks of some type for housing in at least somerespect an appropriate rocket fuel (e.g., hydrazine). One of theserocket fuel storage tanks may function as an initial holding tank ofsorts, while the other of the rocket fuel storage tanks may be thatwhich is directly fluidly interconnected with at least one, and possiblya plurality of, rocket engine modules. Consider the case where the firstand second fluid system components are first and second rocket fueltanks for a space travel vehicle or the like. The valve assemblyassociated with the first aspect of the present invention allows arocket fuel to be directed from a rocket fuel supply system into thefirst rocket fuel tank without directing such rocket fuel into thesecond rocket fuel tank. In this regard, rocket fuel from the rocketfuel supply system may be directed through the first service valve, intothe first chamber of the valve body, out through the inlet and to thefirst fluid conduit fluidly interconnected therewith, and into the firstrocket fuel tank. None of this rocket fuel will be directed to thesecond rocket fuel tank at the time of the “loading” of the first rocketfuel tank due to the isolation which is still being provided between thefirst and second chambers of the valve assembly by the barrier assembly.Rocket fuel may be unloaded from the first rocket fuel tank by reversingthe above-noted flowpath and without directing any of such rocket fuelto the second rocket fuel tank by retaining the integrity of the barrierassembly between the first and second chambers of the valve body.

Continuing with the above-noted example and where the second rocket fueltank is fluidly interconnected with a plurality of rocket enginemodules, the valve assembly associated with the first aspect of thepresent invention also allows an appropriate fluid to be directed intothe second rocket fuel tank (e.g., a gas to keep the second rocket fueltank and/or the rocket engine module(s) fluidly interconnected therewith“clean”). In this regard, an appropriate fluid (e.g., gaseous nitrogen)from a fluid supply system may be directed through the second servicevalve, into the second chamber of the valve body, out through the outletand to the first fluid conduit fluidly interconnected therewith, andinto the second rocket fuel tank and possibly the rocket enginemodule(s) fluidly interconnected therewith. None of this fluid isdirected to the first rocket fuel tank at the time of the “loading” ofthe second rocket fuel tank due to the continued isolation providedbetween the first and second chambers of the valve assembly by thebarrier assembly. This fluid may be “unloaded” from the second rocketfuel tank by reversing the above-noted flowpath and without directingany of such fluid into the first rocket fuel tank by retaining theintegrity of the barrier assembly between the first and second chambersof the valve body.

A second aspect of the present invention is generally directed to afluid transfer system or a system through which fluids may betransferred, and such may be used in combination with the above-notedfirst aspect of the present invention. The second aspect includes firstand second fluid vessels. At least part of the first fluid vesselengages at least part of the second fluid vessel, such as in the case ofa ullage bottle which is disposed within a rocket fuel tank to directrocket fuel (e.g., hydrazine) out of the rocket fuel tank at theappropriate time and through an expansion of the ullage bottle. A firstfluid conduit is fluidly interconnected with the first fluid vessel(e.g., fluid may be directed into and/or out of the first fluid vesselthrough the first fluid conduit), while a second fluid conduit isfluidly interconnected with the second fluid vessel (e.g., fluid may bedirected into and/or out of the second fluid vessel through the secondfluid conduit).

A first valve assembly is associated with the first fluid conduit and asecond valve assembly is associated with the second fluid conduit. Thefirst valve assembly includes a first valve body. A first inlet andfirst outlet extend within the first valve body for directing fluidwithin, out of, and/or through the first valve body. A first chamber isdisposed within the first valve body and is fluidly interconnected withthe first inlet, while a second chamber is disposed within the firstvalve body and is fluidly interconnected with the first outlet.Isolation of the first chamber of the first valve body from the secondchamber of the first valve body, and thereby also the first inlet andfirst outlet, is provided by a first barrier assembly. Prior to aremoval of this isolation by a first barrier rupture assembly associatedwith the subject second aspect, it may be desirable to utilize the firstvalve assembly to direct a flow through a flowpath which includes thefirst chamber of the first valve assembly, first inlet, and a fluidconduit which may be fluidly interconnected therewith, through aflowpath which includes the second chamber of the first valve assembly,first outlet, and the first fluid conduit which is fluidlyinterconnected therewith, or both. In this regard, the first valveassembly also includes a first service port which extends within thefirst valve body, which is fluidly interconnected with the secondchamber of the first valve body both prior to and after any rupturing upthe first barrier assembly, and which receives a first service valvetherein. A service port and service valve could similarly be providedfor the first chamber of the first valve body as well and for generallysimilar purposes.

The second valve assembly is preferably structurally similar to thefirst valve assembly as described, although as will be noted below thelocation of the service port which is required for the second valveassembly of the second aspect differs from the location of the serviceport which is required for the first valve assembly of the secondaspect. Whereas “first” was generally used above to describe structureassociated with the first valve assembly, “second” will generally beused to describe structure associated with the second valve assembly.Prior to a removal of the isolation between the first and secondchambers of the second valve assembly by the second barrier ruptureassembly, it may be desirable to utilize the second valve assembly todirect a flow through a flowpath which includes the first chamber of thesecond valve assembly, second inlet, and the second fluid conduit whichis fluidly interconnected therewith, through a flowpath which includesthe second chamber, second outlet, and a fluid conduit which may befluidly interconnected therewith, or both. In this regard, the secondvalve assembly also includes a second service port which extends withinthe first valve body, which is fluidly interconnected with the firstchamber of the second valve body both prior to and after any rupturingup the second barrier assembly, and which receives a second servicevalve therein. A service port and service valve could similarly beprovided for the second chamber of the second valve body as well and forsimilar purposes. Therefore, the “first service port” associated withthe first valve assembly is associated with its corresponding secondchamber, while the “second service port” associated with the secondvalve assembly is associated with its corresponding first chamber.

Various refinements exist of the features noted in relation to thesecond aspect of the present invention. Further features may also beincorporated in the second aspect of the present invention as well.These refinements and additional features may exist individually or inany combination. For instance, the above-noted first aspect of thepresent invention may be used in combination with the subject secondaspect of the present invention as noted. Moreover, the variouscharacteristics of the valve assembly discussed above in relation to thefirst aspect of the present invention may be used in one or both of thefirst and second valve assemblies associated with the second aspect ofthe present invention as well.

The first fluid vessel of the second aspect of the present invention maybe an expandable and contractable structure (e.g., bellows-like), thesecond fluid vessel may be a least substantially rigid, and the firstfluid vessel may be disposed within the second fluid vessel. Thisarrangement is particularly suited for a rocket fuel application. Rocketfuel within the second fluid vessel may be discharged therefrom bydirecting an appropriate fluid into the first fluid vessel to expand thesame, and thereby reduce the volume of the second fluid vessel which isavailable for rocket fuel storage. This may happen in a number ofdifferent situations. One such situation is when it is desired to unloadthe rocket fuel from the second fluid vessel for purposes other thanoperation of a rocket engine module(s) which may be fluidlyinterconnected with the second fluid vessel. With the first barrierassembly of the first valve assembly and the second barrier assembly ofthe second valve assembly being intact (to isolate their respectivefirst chambers from their respective second chambers), an appropriatefluid may be directed through the first service valve associated withthe first valve assembly, within the second chamber, through the firstoutlet of the first valve assembly since the first barrier assembly isstill isolating the first chamber of the first valve assembly from thesecond chamber of the first valve assembly, through the first conduit,and into the first fluid vessel. Provision of the fluid to the firstfluid vessel in this manner forces rocket fuel within the second fluidvessel out through the second fluid conduit, into the second inlet ofthe second valve assembly, and through the second service valveassociated with the second valve assembly since the second barrierassembly is still isolating the first chamber of the second valveassembly from the second chamber of the second valve assembly. Thisrocket fuel may then be directed by an appropriate conduit to anappropriate rocket fuel supply/storage system or the like. These sameflowpaths may be utilized for loading fuel within the second fluidvessel as well, although in the reverse direction to that noted above.

Another situation where rocket fuel may be discharged from the secondfluid vessel is during operation of one or more rocket engine modules.In this regard, an appropriate fluid supply system (e.g., a pressurizedpneumatics system) may be fluidly interconnected with the first inletassociated with the first valve assembly, while the noted rocket enginemodule(s) may be fluidly interconnected with the second fluid vesselthrough the second fluid conduit and possibly an intermediate fuel tank.Both the first and second barrier rupture assemblies may be activated toallow communication between the first and second chambers of the firstvalve assembly, and further to allow communication between the first andsecond chambers of the second valve assembly. As such, fluid from theabove-noted fluid supply system would be directed through an appropriatefluid conduit to the first inlet of the first valve assembly, throughthe first chamber of the first valve assembly, through the now rupturedfirst barrier assembly, through the second chamber of the first valveassembly, through the second outlet of the first valve assembly, andthrough the first fluid conduit to the first fluid vessel which willhave the above-noted effect on the rocket fuel within the second fluidvessel. The discharge of rocket fuel from the second fluid vessel inthis case will be directed through the second fluid conduit, through thesecond inlet of the second valve assembly, through the first chamber ofthe second valve assembly, through the now ruptured second barrierassembly of the second valve assembly, through the second chamber of thesecond valve assembly, through the second outlet of the second valveassembly, and through an appropriate conduit and again possibly anintermediate fuel tank to the noted rocket engine module(s).

As noted above, the principles of the first aspect of the presentinvention may be used in combination with the subject second aspect ofthe present invention. In this regard and continuing with theabove-noted rocket fuel application of the second aspect of the presentinvention, the system of the second aspect may further include a rocketfuel tank and at least one rocket engine module. The second fluidconduit associated with the second aspect would extend from the secondfluid vessel to the second inlet of the second valve assembly, a thirdfluid conduit would extend from the second outlet of the second valveassembly to the rocket fuel tank, and each rocket engine module would befluidly interconnected with the rocket fuel tank. Therefore, rocket fuelstored in the second fluid vessel would flow through the second fluidconduit, through the second valve assembly, through the third fluidconduit, and to the rocket fuel tank for use by the rocket enginemodule(s) when the barrier assemblies associated with the first andsecond valve assemblies were activated in the above-noted manner. Priorto this activation, the second valve assembly may be utilized to providea flow between the second fluid vessel and a rocket fuel tank, and viceversa, in a manner which will now be described.

The second valve assembly may include a service port which extendswithin the second valve body to interface with the second chamber of thesecond valve assembly as noted above. A third service valve may bedisposed within this particular service port so as to be fluidlyinterconnected with the second outlet of the second valve assemblythrough the second chamber prior to removal of the isolation between thefirst and second chambers of the second valve assembly. This thirdservice valve may be used to direct a flow from a fluid supply system tothe rocket fuel tank, and vice versa, in the manner addressed above inrelation to the first aspect of the present invention (e.g., to providean appropriate gas to the rocket fuel tank and/or rocket fuel enginemodules to keep the same “clean”).

A third aspect of the present invention is directed to a valve whichincludes a valve body, as well as an inlet and an outlet which extendwithin the valve body. A pair of chambers are disposed within the valvebody. One of these chambers is fluidly interconnected with the inlet,while the other of these chambers is fluidly interconnected with theoutlet. A barrier assembly isolates these chambers until a flow throughthe valve is desired. In this regard, the third aspect further includesa barrier rupture assembly for removing this isolation at the desiredtime, which in turn will allow a flow to proceed from the inlet of thevalve body, through the first chamber, through the ruptured barrierassembly, through the second chamber, and through the outlet of thevalve body. Additional flows may be affected by the valve prior to arupturing of its barrier assembly. In this regard, at least one serviceport extends within the valve body and is fluidly interconnected withone of the noted chambers, while at least one service port extendswithin the valve body and is fluidly interconnected with the other ofthese chambers. Service valves may be positioned within the serviceports to direct a flow through only part of the valve prior to removalof the isolation between the noted chambers, and in the manner discussedabove in relation to both the first and second aspects of the presentinvention. Features discussed above in relation to the valve assembliesencompassed by the first and second aspects may be used in this thirdaspect as well.

A fourth aspect of the present invention relates to a service valvewhich provides for either a “flow through” or “no flow” condition inrelation to the service valve, and which may be utilized in either ofthe first, second, and/or third aspects of the present inventiondiscussed above as well. There are a number of important characteristicswhich may be associated with the service valve of the subject fourthaspect due to one or more configurations of the same to be discussed inmore detail below. One such characteristic is that the service valve ofthe fourth aspect need not utilize metal-to-metal seals of any kind, butinstead may utilize at least one and more preferably a plurality ofspaced radial seals. Another characteristic which may be incorporatedinto the service valve of the subject fourth aspect is that may beconfigured so as to provide resistance to side loads, preferably in amanner which avoids any contact between a valve body and a valve stemmovably disposed therein. Yet another characteristic which may beincorporated into the service valve of the subject fourth aspect is thatmay utilize redundant seals on redundant sealing surfaces.

A first embodiment of the fourth aspect of the present inventionincludes a valve body with a valve body bore therewithin. This valvebody is integrally formed in that is formed from a single piece ofmaterial such that there is no joint of any kind therewithin, at leastin relation to those surfaces of the valve body which define at leastcertain portions of its bore. Disposed within this valve body bore is avalve stem which is movable between at least two positions. One of thesevalve stem positions allows for a flow through the service valve (a“flow through” condition), while the other of these valve stem positionsprecludes any such flow through the service valve (a “no flow”condition). Flow through the service valve may be provided by fluidlyinterconnecting the valve body bore with a valve stem bore which mayextend through the valve stem. In this case the two noted conditions maybe affected by providing a removable cap for an end of the valve stemwhich extends beyond the valve body. When the cap covers the valve stembore, the service valve is in its “no flow” condition. Conversely, whenthe cap “uncovers” or is off the valve stem bore, the service valve isin its “flow through” condition. There may be other ways to affect a“flow through” and a “no flow” condition for the service valve bymovement of the valve stem through the valve body.

Movably interconnecting the valve body and valve stem introduces a firstleakpath between these two structures. In one embodiment this is theonly leakpath within the service valve of the subject first embodimentof the fourth aspect of the present invention. Flow along/through thisfirst leakpath is addressed by a plurality of radial seals which arespaced along an extent of this first leakpath. Each of these radialseals may be mounted on either the valve body or the valve stem. Atleast three radial seals engage both the valve body and valve stem, whenthe valve stem is positioned to provide a “no flow” condition for theservice valve, so as to at least impede, and more preferably toterminate, any flow into/along the first leakpath at three spacedlocations. At least two radial seals engage both the valve body andvalve stem, when the valve stem is positioned to provide a “flowthrough” condition for the service valve, so as to at least impede, andmore preferably to terminate, flow into/along at least a portion of thefirst leakpath at two spaced locations.

Various refinements exist of the features noted in relation to the firstembodiment of the fourth aspect of the present invention. Furtherfeatures may also be incorporated in the first embodiment of the fourthaspect of the present invention as well. These refinements andadditional features may exist individually or in any combination. Thebore within the valve body may be defined by an inner wall whichincludes first, second and third wall sections. Each of these three wallsections defines a portion of a length dimension of the bore, with eachpreferably then being at least generally longitudinally extending. Thesefirst, second, and third wall sections may be disposed in end-to-endrelation, or there may be intermediate structure between the first andsecond wall sections and/or between the second and third wall sections,such as an appropriately configured transition section (e.g., achamfered surface). In any case, the second wall section is disposed atleast somewhere longitudinally between the first and third wallsections.

Each of the above-noted second and third wall sections may be at leastgenerally cylindrical surfaces of different diameters. The first wallsection may also be a cylindrical surface and may be of a differentdiameter than the second wall section. One embodiment has the first wallsection at a smaller diameter than the second wall section, and thesecond wall section at a smaller diameter than the third wall section.In any case, a first radial seal may be disposed between and engage boththe first wall section of the valve body and valve stem when the valvestem is in positioned to provide a “no flow” position for the servicevalve, but may be disengaged with one of the first wall section of thevalve body and valve stem so as to provide for a flow through theservice valve by an appropriate movement of the valve stem relative tothe valve body to another position. Engagement of first radial seal withboth the first wall section of the valve body and valve stem may becharacterized as defining the valve seat of the first embodiment of thisfourth aspect of the present invention. A second radial seal may at alltimes be disposed between and engaged with both the second wall sectionof the valve body and the valve stem, while a third radial seal may alltimes be disposed between and engaged with both the third wall sectionof the valve body and the valve stem. The second and third radial sealsprovide a redundant sealing feature, for blocking the first leakpathbetween the valve body and the valve stem, in both the “flow through”and “no flow” conditions for the service valve. The effectiveness ofhaving these redundant seals is enhanced by having the second and thirdwall sections be of different diameters. This significantly reduces thepotential for an imperfection existing within the inner wall whichdefines the bore and which would adversely affect the ability of boththe second and third radial seals to effectively terminate further flowdownstream thereof through the first leakpath.

Having a plurality of longitudinally spaced radial seals between and inengagement with each of the valve body and the valve stem providesbenefits other than redundant seals. These same seals also provideanother function, that of maintaining the valve body and valve stem inspaced relation. Preferably, the valve body and valve stem aremaintained in spaced relation even when the service valve of the subjectfirst embodiment of the fourth aspect is exposed to a shear or sideload. For instance, the valve body and valve stem may be maintained inspaced relation (i.e., so as to avoid contact therebetween), when aradially-directed side load (i.e., at least somewhat transverse to thelongitudinal extent of the valve) of at least about 25 pounds is appliedto the service valve, such as a portion of the valve stem which mayextend beyond the valve body. Application of a side load to the valvestem, when the valve stem is disposed relative to the valve body toprovide a “no flow” condition for the service valve, may result in atleast one of these radial seals functioning as a fulcrum so as tokeep/prevent the valve stem from contacting the valve body. Anotherradial seal(s) may function as fulcrum(s) so as to keep/prevent thevalve stem from contacting the valve body when a side load is applied tothe valve stem with the valve stem being disposed relative to the valvebody to provide a “flow through” condition for the service valve.Consider the example presented above where the plurality of radial sealswere noted to possibly include first, second, and third radial seals.The second and/or third radial seals may each function as such a fulcrumwhen the valve stem is disposed to provide a “flow through” conditionfor the service valve, while the first radial seal may function as sucha fulcrum when the valve stem is disposed to provide a “no flow”condition for the service valve.

A second embodiment of the fourth aspect of the present inventionincludes a valve body with an at least generally longitudinallyextending valve body bore in which a valve stem is movably disposed soas to provide for both a “flow through” and a “no flow” condition forthe service valve. The bore within the valve body is defined by an innerwall. Multiple and distinct longitudinal segments or wall sectionsdefine this bore-defining inner wall. First, second, and third wallsections of the inner wall each have a longitudinal extent or lengthdimension, and may be disposed in end-to-end relation or there may beintermediate structure between the first and second wall sections and/orbetween the second and third wall sections, such as an appropriatelyconfigured (e.g., chamfered) transition section. In any case, the secondwall section is disposed at least somewhere longitudinally between thefirst and third wall sections.

Each of the above-noted second and third wall sections of the subjectsecond embodiment of the fourth aspect are at least generallycylindrical surfaces of different diameters. The first wall section mayalso be a cylindrical surface and may be of a different diameter thanthe second wall section. One embodiment has the first wall section at asmaller diameter than the second wall section and the second wallsection at a smaller diameter than the third wall section for a casewhere the valve stem is moved in a direction which is at least generallylongitudinally away from the first wall section to provide a “flowthrough” condition for the service valve. In any case and including thislater variation, a first radial seal is disposed between and engagesboth the first wall section of the valve body and valve stem when thevalve stem is disposed to provide a “no flow” condition for the servicevalve, but is disengaged with one of the first wall section of the valvebody and valve stem so as to provide for a flow within/through theservice valve by an appropriate movement of the valve stem relative tothe valve body. Engagement of the first radial seal with both the firstwall section of the valve body and valve stem may then be properlycharacterized as defining the valve seat of the subject secondembodiment of this fourth aspect of the present invention. A secondradial seal is at all times disposed between and engages both the secondwall section of the valve body and the valve stem, while a third radialseal is at all times disposed between and engages both the third wallsection of the valve body and the valve stem.

The above-noted second and third radial seals provide redundancy forblocking a leakpath between the valve body and the valve stem, in boththe “flow through” and “no flow” conditions for the service valve. Theeffectiveness of this redundancy is enhanced by having the second andthird wall sections be of different diameters. That is, thisconfiguration significantly reduces the potential for an imperfectionexisting within the inner wall which defines the bore within the valvebody and which would adversely affect the ability of both the second andthird radial seals to effectively terminate further flow downstreamthereof in an area between the inner wall of the valve body and thevalve stem.

Each of those features discussed above in relation to the firstembodiment of the subject fourth aspect may be used individually or inany combination in this second embodiment of the fourth aspect as well.

A third embodiment of the fourth aspect of the present inventionincludes a valve body with a valve body bore therewithin. Disposedwithin this valve body bore is a valve stem which is movable between atleast two positions. One of these valve stem positions allows for a flowthrough the service valve, while the other of these valve stem positionsprecludes any such flow through the service valve. Movablyinterconnecting the valve body and valve stem introduces a firstleakpath between these two structures, which is the only leakpath withinthe service valve in the case of the third embodiment of the subjectfourth aspect. Flow along/through this first leakpath is addressed by aplurality of radial seals which are spaced along an extent of this firstleakpath. Each of these radial seals may be mounted on either the valvebody or the valve stem. At least three radial seals engage both thevalve body and valve stem when the valve stem is disposed to provide a“no flow” condition for the service valve. These 3 radial seals therebyfunction to at least impede, and more preferably to terminate, any flowinto/along the first leakpath at least at three spaced locations when noflow is being directed through the service valve. At least two radialseals engage both the valve body and valve stem when the valve stem isdisposed to provide a “flow through” condition for the service valve.These 2 radial seals thereby function to at least impede, and morepreferably to terminate, flow into/along at least a portion of the firstleakpath at two spaced locations while there is flow through the servicevalve.

Each of those features discussed above in relation to the firstembodiment of the subject fourth aspect may be used individually or inany combination in this third embodiment of the fourth aspect as well.

A fourth embodiment of the fourth aspect of the present inventionincludes a valve body with a valve body bore therewithin. Disposedwithin this valve body bore is a valve stem which is movable between atleast two positions. One of these valve stem positions allows for a flowthrough the service valve, while the other of these valve stem positionsprecludes any such flow through the service valve. Movablyinterconnecting the valve body and valve stem introduces a firstleakpath between these two structures. Flow along/through this firstleakpath is addressed by a plurality of radial seals which are spacedalong an extent of this first leakpath. Each of these radial seals maybe mounted on either the valve body or the valve stem. At least threeradial seals engage both the valve body and valve stem when the valvestem is disposed to provide a “no flow” condition for the service valve.These 3 radial seals thereby function to at least impede, and morepreferably to terminate, any flow into/along the first leakpath at leastat three spaced locations when no flow is being directed through theservice valve. At least two radial seals engage both the valve body andvalve stem when the valve stem is disposed to provide a “flow through”condition for the service valve. These 2 radial seals thereby functionto at least impede, and more preferably to terminate, flow into/along atleast a portion of the first leakpath at two spaced locations whilethere is flow through the service valve. In addition to providing thenoted sealing function, the plurality of radial seals also maintain thevalve body and valve stem in spaced relation.

Each of those features discussed above in relation to the firstembodiment of the subject fourth aspect may be used individually or inany combination in this fourth embodiment of the fourth aspect as well.

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWING

FIG. 1 is a perspective view of one embodiment of a multifunctionalvalve with multiple flowpaths therethrough.

FIG. 2 is another perspective view of the multifunctional valve of FIG.1.

FIG. 3 is a top view of the multifunctional valve of FIG. 1.

FIG. 4 is a cross-sectional view of the multifunctional valve of FIG. 3,taken along line 4—4.

FIG. 5 is a schematic of one embodiment of a reaction control systemwhich includes a number of multifunctional valves of the type presentedin FIGS. 1-4.

FIG. 6 is another schematic of the embodiment of the reaction controlsystem presented in FIG. 5.

FIG. 7 is a perspective view of one embodiment of a service valve whichmay be used in the reaction control system of FIGS. 5-6.

FIG. 8 is a side view of the service valve of FIG. 7.

FIG. 9 is a cross-sectional view of the service valve of FIG. 7, takenalong its longitudinal extent.

FIG. 10 is an exploded, perspective view of the service valve of FIG. 7.

DETAILED DESCRIPTION OF THE INVENTION

The present invention will now be described in relation to theaccompanying drawings which at least assist in illustrating its variouspertinent features. FIGS. 1-4 illustrate one embodiment of themultifunctional valve 10. Generally, the valve 10 functions to allowfluid to flow from one side of the valve to the other side of the valveat a desired or selected time. Such a valve is particularly useful inlaunch vehicle or spacecraft applications where highly volatile fluids(e.g., hypergolic fluids, such as hydrazine) are utilized. Such valves10 also facilitate servicing of certain components of reaction controlsystems of which the valves of the present invention are included. Morespecifically, in one embodiment, illustrated in FIGS. 1-4, the valve 10includes inflow and outflow tubes or flow passageways 20,30,respectively, adapted to allow a fluid to flow therethrough, a valvebody 40 having first and second chambers or cavities 42, 44,respectively, which are in fluid communication with the inflow andoutflow passageways 20,30, respectively, the first and second cavities42, 44 being defined in part by a first wall or partition or barrierassembly 46, first and second service ports 50,60, respectively capableof receiving first and second service valves through which a fluid maybe flowed inwardly or outwardly relative to the valve 10, depending uponthe application, and a barrier rupture or separation assembly 70 foropening the valve 10 to allow fluid to flow through the valve 10, andspecifically, from the first cavity 42 to the second cavity 44 of thevalve body member 40, such that the inflow and outflow passageways 20,30 are in fluid communication with each other via the valve body member40 after initiation of the separation assembly 70.

In particular, the first partition 46 initially functions to inhibitfluid communication between the first and second chambers or cavities42,44, respectively, until ruptured, separated, or severed by theseparation assembly 70. As such, the first partition 46 allows certaincomponents in fluid communication with the valve 10 to be serviced viathe first and/or second service ports 50, 60 and service valves whichare engagable with such service ports 50, 60 (which will be described inmore detail hereinbelow). In this embodiment, the separation wall orpartition 46 comprises first and second sections 46 a, 46 b which areintegrally formed with the valve body member 40. In an alternativeembodiment, the separation wall 46 may comprise a single wall separatingthe first and second cavities or chambers 42, 44. In order to providefor fluid communication between the first and second cavities 42,44 uponinitiation of the separation assembly 70, in the present embodiment, theseparation assembly 70 includes first and second trigger bodies 72 a, 72b each having an initiator and a cartridge with an explosive charge, andfirst and second rams 74 a, 74 b which, upon initiation and explosion ofthe trigger bodies 72 a, 72 b, are rammed against the first and secondsections 46 a, 46 b, respectively, of the separation wall 46 to rupture,separate or break the first and second sections 46 a, 46 b,respectively, to thereby allow fluid communication between the first andsecond cavities 42, 44. Valve 10 includes first and second triggerbodies 72 a, 72 b and corresponding rams 74 a, 74 b for purposes ofredundancy (e.g., in the event one of the trigger bodies 72 a, 72 bfails to fire, the other breaks the corresponding separation wall 46 a,46 b to achieve fluid communication between the first and secondcavities 42,44). However, a single trigger body and a single ram may beutilized to fluidly connect the first and second cavities 42,44, tothereby allow fluid to flow from the inflow tube 20 to the outflow tube30.

As indicated hereinabove, the valve 10 may be utilized in certain launchvehicle and spacecraft applications, and in particular, for reactioncontrol service systems associated with such. For example, themultifunctional valve may be utilized in an upper stage, which isutilized to steer to a spacecraft after separation of the spacecraftfrom the launch vehicle or booster rocket. In one embodiment, theschematic of which is illustrated in FIGS. 5-6, a first multifunctionalvalve 110 (similarly structured to the valve 10) functions as apneumatic valve adapted to at least pressurize and/or depressurize anullage bottle 186 of a storage bottle 184 capable of storing a fluid,such as a rocket fuel (e.g., hydrazine). A second multifunctional valve210 (similarly structured to the valve 10) is positionable downstreamthe storage bottle 184 and functions as a liquid valve to at least filland/or remove such fluid, such as hydrazine, from the storage bottle184. More specifically, the valve 110 positioned upstream of the storagebottle 184 is adapted to assist in the servicing of the storage bottle184 and to pressurize such storage bottle 184 upon initiation or firingof the valve 110 in order to force the fluid contained within thestorage bottle 184 to flow to a tank 182 via the liquid valve 210, whichwill be described in more detail hereinbelow.

The valve 110 includes a valve body member 140 having first and secondchamber 142, 144, respectively, which are in fluid communication withinflow and outflow tubes or passageways 120, 130. The inflow passage 120is interconnectable to (e.g, in fluid communication with) a fluid supplysystem 192 by a conduit 194. The fluid supply system 192 is capable ofsupplying a fluid, such as a gas (e.g., pressurized gaseous helium), tothe ullage bottle 186 upon initiation of the valve 110 via the outflowpassageway 130 and a fluid conduit 200 which extends between and fluidlyinterconnects the outflow passageway 130 and the ullage bottle 186. Thevalve 110 further includes triggers or initiators 172 a, 172 b which,when fired, open the valve 110 so that fluid, such as the pressurizedgaseous helium from the fluid supply system 192 (e.g., helium source)may flow from through the valve 110 into the ullage bottle 186. In thisregard, the valve 110 also includes at least a first wall or partition146 (which includes first and second sections 146 a, 146 b, againprincipally for redundancy) between the first and second cavities 142,144 which breaks, separates, or otherwise ruptures upon firing of thetriggers or initiators 172 a, 172 b to open the valve 110 (i.e., toremove the isolation between the first chamber 142 and the secondchamber 144). For launch vehicle and spacecraft applications, suchinitiation or firing typically occurs after the launch vehicle hasseparated from the spacecraft and associated upper stage, the reactioncontrol system 100 illustrated in FIGS. 5-6 being associated with suchupper stage.

For purposes of allowing servicing of the pneumatic portion of thesystem 100 prior to launching of such a spacecraft (e.g., on the launchpad), the valve 110 includes a service port 160 which is associated withthe second chamber 144 and which is used to pressurize and/ordepressurize the ullage bottle 186 (a service port 150 of the valve 110is associated with the first chamber 142, and is not used by thereaction control system 100). For instance, in a ground environment,prior to the launch, a vacuum system 196 may be interconnected to theservice port 160 via a fluid conduit 199 and a service valve 310 a whichis disposed within the service port 160. A preferred configuration forthe service valve 310 a is described in more detail below in relation toFIGS. 7-10. Other configurations of services valves 310 a could be usedby the reaction control system 100. For instance, commercially availablevalves from Moog and OEA, Inc., which utilize a metal-to-metal seal(e.g., metal ball against a metal channel) to close or seal the valvecould be used as well.

The vacuum system 196 may be activated to create a vacuum in the ullagebottle 186 to assist in the filling of the storage bottle 184 with theselected fluid, such as hydrazine, such fluid being introduced into thestorage bottle 184 via a service port 250 associated with the liquidvalve 210 as will be discussed below. Isolation of the first chamber 142from the second chamber 144 in this case allows a vacuum to be drawnusing a flowpath which includes the ullage bottle 186, the fluid conduit200, the outflow tube 130, the second chamber 144, the service valve 310a, and the fluid conduit 199 (i.e., this particular flowpath does notinclude the first chamber 142 since the same is still isolated from thesecond chamber 144 in this instance). The service port 160 may also beutilized to pressurize the ullage bottle 186 to unload or empty thefluid (e.g., hydrazine) from the storage bottle 186 (e.g., in a groundenvironment, and prior to launch), whereby the ullage bottle 186 iscaused to expand within the storage bottle 184 to force the fluid out ofthe storage bottle 184 via the service port 250 associated with thevalve 210 as will be discussed below. In this regard, the reactioncontrol system 100 further includes a first fluid supply/storage system198 (e.g., a supply of an appropriate pressurized fluid such as helium)which is also fluidly interconnected with the service valve 310 a, andthereby the second chamber 144 of the valve 110, via the fluid conduit199. Isolation of the first chamber 142 from the second chamber 144 inthis case allows an appropriate pressurized fluid to be directed fromthe first fluid supply/storage system 198 to the ullage bottle 184through a flowpath which includes the fluid conduit 199, the servicevalve 310 a, the second chamber 144, the outflow tube 130, and the fluidconduit 200 (i.e., this particular flowpath does not include the firstchamber 142 since the same is still isolated from the second chamber 144in this instance).

As noted hereinabove, the multifunctional valve 210 may also be utilizedto allow the transfer of a fluid, such as hydrazine, from the storagebottle 186 into a tank bottle 182 via a fluid conduit 204, the valve210, and a fluid conduit 202. In spacecraft applications, the tankbottle 182 may be in fluid communication with a plurality of rocketengine modules 180 a-180 d which may be utilized on the upper stage tosteer such upper stage when fired (e.g., after separation of the upperstage and spacecraft interconnected thereto from the launch vehicle orbooster rocket). In order to facilitate such a transfer of fluid withinthe storage bottle 184 into the tank bottle 182 for use by the rocketengine modules 180 a-180 d, the multifunctional valve 210 includestriggers or initiators 272 a, 272 b which are adapted to drive first andsecond rams 274 a, 274 b, respectively, into at least a first separationwall or partition 246 (which again includes first and second sections246 a, 246 b, principally for redundancy). The first separation wall 246isolates first and second cavities 242,244 within the valve body 240 ofthe valve 210, with the first chamber or cavity 242 always being fluidlyinterconnected with an inflow tube or passageway 220 of the valve 210,and with the second chamber or cavity 244 always being fluidlyinterconnected with an outflow tube or passageway 230 of the valve 210.The first partition 246 thus inhibits fluid flow through the valve 210until broken or otherwise ruptured by the first and/or second rams 274a, 274 b (e.g., upon firing of the initiators 272 a, 272 b)). As notedhereinabove with respect to another embodiment, like the valve 110, thevalve 210 includes first and second initiators 272 a, 272 b,respectively, for redundancy in the event one of the initiators ortriggers fails to fire. In use, upon simultaneous firing of theinitiators 172 a, 172 b and 272 a, 272 b of the valves 110,210,respectively, pressurized fluid (e.g., helium at 450 psi) from the fluidsupply system 192 is allowed to enter and fill the ullage bottle 186 viathe opened valve 110, which forces the hydrazine or other fluidcontained within the storage bottle 184 to exit the storage bottle 184and flow into the tank bottle 182 via the fluid conduit 204, the openedvalve 210, and the fluid conduit 202 in order to make such fluidavailable for use by the rocket engine modules 180 a-180 d.

The valve 210 further includes a bottle liquid service port 250 which,in ground applications, allows the storage bottle 184 to be filled withhydrazine fluid or other fluids, and also allows such fluids to beremoved from the storage bottle 184. In this regard, a service valve 310b is disposed within the service port 250. A fluid conduit 280 fluidlyinterconnects the service valve 310 b with a fuel/supply storage system278. Fluid may be transferred between the storage bottle 184 and thefuel supply/storage system 278, prior to activation of the valve 210(i.e., with the first chamber 242 continuing to be fluidly isolated fromthe second chamber 244), through a flowpath which thereby includes thefluid conduit 280, the service valve 310 b, the first chamber 242, theinflow passageway 220, and the fluid conduit 204 (i.e., this particularflowpath does not include the second chamber 244 since the same is stillisolated from the first chamber 244 in this instance).

The valve 210 further includes a loop service port 260 which is adaptedto introduce a fluid, such as gaseous nitrogen, into the tank bottle 182to keep the tank bottle 182 and/or rocket engine modules 180 a-180 dclean. The loop service for 260 may also be utilized to remove thegaseous nitrogen from the tank bottle 182 as well. In this regard, aservice valve 310 c is disposed within the service port 260. A fluidconduit 286 fluidly interconnects the service valve 310 c with a secondfluid supply/storage system 284. A appropriate fluid may be transferredbetween the fuel tank 182/rocket engine modules 180 a-d and the secondfluid supply/storage system 284, prior to activation of the valve 210(i.e., with the first chamber 242 continuing to be fluidly isolated fromthe second chamber 244), through a flowpath which thereby includes thefluid conduit 286, the service valve 310 c, the second chamber 244, theoutflow passageway 230, and the fluid conduit 202 (i.e., this particularflowpath does not include the first chamber 242 since the same is stillisolated from the first chamber 142 in this instance).

For purposes of providing analytical data, the multifunctional valves110, 210 pressure transducers 190, 290 which are in fluid communicationwith the outflow passageways 130, 230, respectively, to measure thepressure of the fluid flowing out of the valves 110, 210, respectively.Other pressure transducers could be in fluid communication with theinflow passageways 120,220, respectively, to measure the pressure of thefluid flowing into the valves 110,210, respectively (not shown).

The multifunctional valves 110,210 are particularly useful in thereaction control system 100 for initially inhibiting the flow ofvolatile fluids, such as hydrazine, into the tank bottle 182 and rocketengine modules 180 a-180 d since any leakage of such volatile fluidsfrom the tank bottle 182 or rocket engine modules 180 a-180 d couldadversely effect (e.g., corrode) portions of the launch vehicle orbooster, or spontaneously explode upon contact with certain materials,(e.g., copper), and since such fluids may be poisonous. In this regard,the valves 110, 210 may be fabricated from a material which iscompatible with hydrazine, such as corrosion resistant steel (e.g., 321cres, 304 cres, 316 cres, etc.). The multifunctional valves 110, 210 mayalso be fabricated from other materials, such as polymers or Teflon,depending upon the application and fluid being utilized.

As noted hereinabove, service valves 310 may be interconnected to theports (e.g., ports 50, 60 of the valve 10, ports 150,160 of the valve110, and ports 250,260 of the valve 210) for purposes of servicing thereaction control system 100, or any other system interconnected to themultifunctional valves 10, 110, 310. Such service valves 310 generallyfunction to allow and inhibit fluid communication (e.g., open and close)between a fluid source or receptacle, and the system being serviced(e.g., the reaction control system 100). One embodiment of the types ofservices valves 310 a-c used by the above-noted reaction control system100 is illustrated in FIGS. 7-10 in the form of the valve 310. Theservice valve 310 is operably interfacial with a body member 320 andgenerally includes a stem 330 which is slidably engagable with the bodymember 320, a nut member 340 for moving the stem 330 axially relative tothe body member 320 to open and close the valve, in cooperation with asnap ring 350, and a cap 360 which is engagable with an end portion ofthe stem 330. More specifically, the body member 320 includes an axiallyextending channel 322 through which a fluid may flow when the valve 310is open. In this embodiment, the channel 322 includes first, second andthird stepped walls 324 a, 324 b, 324 c having first, second and thirddiameters, respectively. Such walls 324 a, 324 b, 324 c of the bodymember 320 are abuttingly engagable with first, second and third O-ringsor sealing members 334 a, 334 b, 334 c which are receivable withinannular grooves 332 a, 332 b, 332 c, respectively, of the stem 330. Suchabutting engagement between the sealing members 334 a, 334 b, 334 c withthe stepped walls 324 a, 324 b, 324 c of the body member 320,respectively, function not only to inhibit the flow of a fluid throughthe valve 310 (i.e., to close the valve 310), but also function toinhibit metal-to-metal contact between surfaces of the stem 330 and thebody member 320 when subjected to shear loads. Such first, second andthird seals 334 a, 334 b, 334 c provide redundancy to inhibit leakage ofa fluid there through. Such seals also function to preserve thecleanliness of the valve 310 since contaminants may react adversely whenin contact with certain fluids, such as hydrozene. A fourth sealingmechanism is provided by the cap 360 which is threadedly engagable withan end portion of the stem 330. In one embodiment, where the servicevalve 310 will be interconnected to a multifunctional valve 10, 110,210, the body member 320 may be integrally formed as part of the valves10, 110, 210.

The sealing function is performed by redundant radially sealed O-rings(e.g., seals 334 a-334 c) on redundant sealing surfaces (e.g., steppedwalls 324 a-324 c). If the o-rings are damaged, they can be easilyreplaced by simply removing the stem 330. Once the retaining nut 340closes the flow passage, the sealing effectively is independent ofclosing torque applied.

In operation, when a tank interconnected to the body member 320 is to befilled with a fluid, such as hydrazine, the nut 340 may be rotated, suchthat the end portion 342 of the nut member 340 abuttingly engages thesnap ring 350 to push the snap ring 350 and consequently, the stem 330,axially relative to the body member 320 to open the valve 310. Morespecifically, as the nut member 340 is rotated, an end portion 342 ofthe nut member pushes against the snap ring 350 to partially withdrawthe stem 330 from the channel 322 of the member 320. As the stem 330 isaxially withdrawn, the sealing member 334 a loses abutting engagementwith the first stepped wall 324 a which allows fluid entering the endportion 36 of the stem 330 to flow through the passageway defined by thefirst stepped wall 324 a of a body member 320, and through the channel322 to a tank. Once the tank is filled with the fluid, the cap 360 maybe threaded onto the stem member 330 to provide a redundant seal and tomaintain cleanliness within the valve 310, and the nut member 340 may berotated to push the stem 330 back into the body member 320, such thatthe sealing member 334 a is in abutting engagement with the firststepped wall 324 a to seal the valve 310. Such rotation of the nut 340also results in the abutting engagement of a second and third sealingmember 334 b, 334 c with the second and third stepped walls 324 b, 324c, respectively, to provide additional redundancy in sealing the valve310. The nut member 340 may be rotated in threaded engagement with thebody member 320 until the surface 344 of the nut engages the surface 326of a body member 320, which prevents over-torquing.

When in an open configuration, fluid may flow through the channel 338defined by the inner wall surface of the stem 330 and through the ports339 a, 339 b, 339 c and 339 d, the fluid then being flowable through thechannel 322 of the body member 320. The ports 339 a-339 d may bepositioned 90 degrees relative to each other, about the end portion ofthe stem 330.

As noted, the first, second, and third sealing members 334 a, 334 b, and334 c function not only to inhibit flow of a fluid through the valve310, but also to inhibit metal-to-metal contact between surfaces of thestem 330 and the body member 320 when subjected to shear loads. Statedanother way, the first, second and third sealing members 334 a, 334 b,and 334 c maintain the body member 320 and stem 330 in spaced relation,even when the valve 310 is subjected to shear loads. One way ofcharacterizing the degree of multi-functionality possessed by theservice valve 310 is that the design of the service valve 310 (e.g., thesize of the sealing members 334 a-c, the resiliency of these sealingmembers 334 a-c, the spacing between the wall of the body member 320which defines the channel 322 and the exterior of the stem 330, thespacing between the various sealing members 334 a-c) is such that thebody member 320 and stem 330 are maintained in spaced relation, evenwhen the valve 310 is exposed to a shear load of at least about 25pounds (e.g., a load applied to that portion of the stem 330 whichextends beyond the body member 320 and which is directed at leastgenerally toward a longitudinal axis of the valve 310 which extendscentrally through the channel member 322). Specific characteristics ofthe design of the valve 310 which allow the sealing members 334 a-c toprovide a sealing function, as well as to maintain the body member 320and stem 330 in spaced relation include using compressed elastomericseals, using multiple redundant seals, using multiple redundant sealingsurfaces, and specific tight dimensional tolerances, such as ±0.001inches.

The foregoing description of the present invention has been presentedfor purposes of illustration and description. Furthermore, thedescription is not intended to limit the invention to the form disclosedherein. Consequently, variations and modifications commensurate with theabove teachings, and skill and knowledge of the relevant art, are withinthe scope of the present invention. The embodiments describedhereinabove are further intended to explain best modes known ofpracticing the invention and to enable others skilled in the art toutilize the invention in such, or other embodiments and with variousmodifications required by the particular application(s) or use(s) of thepresent invention. It is intended that the appended claims be construedto include alternative embodiments to the extent permitted by the priorart.

What is claimed is:
 1. A fluid transfer system, comprising: first andsecond fluid system components; a first fluid conduit which fluidlyinterconnects said first and second fluid system components; a valveassembly which is disposed within said first fluid conduit and whichcomprises: a valve body; an inlet and outlet which extend within saidvalve body and which are fluidly interconnected with said first fluidconduit; first and second chambers which are disposed within said valvebody and which are fluidly interconnected with said inlet and outlet,respectively; a barrier assembly which is disposed within said valvebody and which isolates said first chamber from said second chamber; abarrier rupture assembly which is interconnected with said valve bodyand which is directed toward said barrier assembly; first and secondservice ports which extend within said valve body and which are fluidlyinterconnected with said first and second chambers, respectively; afirst service valve which is disposed within said first service port andwhich is thereby fluidly interconnected with said first chamber; and asecond service valve which is disposed within said second service portand which is thereby fluidly interconnected with said second chamber. 2.A system, as claimed in claim 1, wherein: said first and second fluidsystem components comprise first and second rocket fuel storage vessels,respectively.
 3. A system, as claimed in claim 2, wherein: said firstrocket fuel storage vessel comprises a supply of hydrazine.
 4. A system,as claimed in claim 2, wherein: said first rocket fuel storage vesselcomprises a storage bottle and said second rocket fuel storage vesselcomprises a rocket fuel tank, wherein said rocket fuel tank is fluidlyinterconnected with at least two rocket engine modules.
 5. A system, asclaimed in claim 2, wherein: upon actuation of said barrier ruptureassembly, rocket fuel flows from said first rocket fuel storage vessel,through said first fluid conduit and past said valve assembly, and tosaid second rocket fuel storage vessel.
 6. A system, as claimed in claim5, wherein: said rocket fuel flows through said inlet of said valveassembly, through said first chamber of said valve assembly, throughsaid barrier assembly which has been ruptured by said barrier ruptureassembly, through said second chamber of said valve assembly, throughsaid outlet of said first valve assembly, and through a portion of saidfirst fluid conduit which is disposed between said valve assembly andsaid second rocket fuel storage vessel.
 7. A system, as claimed in claim1, wherein: said barrier assembly comprises at least one partition.
 8. Asystem, as claimed in claim 7, wherein: said at least one partition isintegrally formed with said valve body.
 9. A system, as claimed in claim7, wherein: said at least one partition comprises separate first andsecond partitions which are spaced from each other.
 10. A system, asclaimed in claim 1, wherein: said barrier rupture assembly comprises atleast one initiator and at least one projectile.
 11. A system, asclaimed in claim 1, wherein: said barrier rupture assembly comprises afirst initiator and a corresponding first projectile, as well as asecond initiator and a corresponding second projectile.
 12. A system, asclaimed in claim 1, wherein: said first service valve may be used toprovide a fluid to said first fluid system component through said valveassembly and prior to a rupturing of said barrier assembly by directingsaid fluid through said first service valve, through said inlet, andthrough a portion of said first fluid conduit which fluidlyinterconnects said valve assembly and said first fluid system component.13. A system, as claimed in claim 1, wherein: said second service valvemay be used to provide a fluid to said second fluid system componentthrough said valve assembly and prior to a rupturing of said barrierassembly by directing said fluid through said second service valve,through said outlet, and through a portion of said first fluid conduitwhich fluidly interconnects said valve assembly and said second fluidsystem component.
 14. A system, as claimed in claim 1, furthercomprising: a rocket fuel supply system which is fluidlyinterconnectable with said valve assembly through said first servicevalve, wherein said first fluid system component comprises a firstrocket fuel storage vessel, wherein a rocket fuel may be transferredbetween said rocket fuel supply system and said first rocket fuelstorage vessel via a first flowpath prior to a rupturing of said barrierassembly, wherein said first flowpath comprises said first chamber andsaid inlet of said valve assembly, and wherein said second chamber ofsaid valve assembly is not part of said first flowpath.
 15. A system, asclaimed in claim 1, further comprising: a plurality of rocket enginemodules which are fluidly interconnected with said second fluid systemcomponent, wherein said second fluid system component comprises a rocketfuel tank; and a pressurized gas supply system which is fluidlyinterconnectable with said valve assembly through said second servicevalve, wherein a gas from said pressurized gas supply system may betransferred between said pressurized gas supply system and said rocketfuel tank via a first flowpath prior to a rupturing of said barrierassembly, wherein said first flowpath comprises said second chamber andsaid outlet of said valve assembly, and wherein said first chamber ofsaid valve assembly is not part of said first flowpath.
 16. A system, asclaimed in claim 1, further comprising: a first pressure transducerwhich is interconnected with said valve body and which is fluidlyinterconnected with at least one of said first chamber and said secondchamber of said valve assembly.
 17. A fluid transfer system, comprising:a first fluid vessel; a second fluid vessel, wherein at least part ofsaid first fluid vessel engages at least part of said second fluidvessel; a first fluid conduit which is fluidly interconnected with saidfirst fluid vessel; a second fluid conduit which is fluidlyinterconnected with said second fluid vessel; a first valve assemblywhich comprises: a first valve body; a first inlet and outlet whichextend within said first valve body; first and second chambers which aredisposed within said first valve body and which are fluidlyinterconnected with said first inlet and outlet, respectively; a firstbarrier assembly which is disposed within said first valve body andwhich isolates said first chamber of said first valve assembly from saidsecond chamber of said first valve assembly; a first barrier ruptureassembly which is interconnected with said first valve body and which isdirected toward said first barrier assembly; a first service port whichextends within said first valve body and which is fluidly interconnectedwith said second chamber of said first valve assembly; and a firstservice valve which is disposed said first service port of said firstvalve assembly and which is thereby fluidly interconnected with saidsecond chamber of said first valve assembly, wherein said first fluidconduit extends between said first fluid outlet of said first valveassembly and said first fluid vessel; and a second valve assembly whichcomprises: a second valve body; a second inlet and outlet which extendwithin said second valve body; first and second chambers which aredisposed within said second valve body and which are fluidlyinterconnected with said second inlet and outlet, respectively; a secondbarrier assembly which is disposed within said second valve body andwhich isolates said first chamber of said second valve assembly fromsaid second chamber of said second valve assembly; a second barrierrupture assembly which is interconnected with said second valve body andwhich is directed toward said second barrier assembly; a second serviceport which extends within said second valve body and which is fluidlyinterconnected with said first chamber of said second valve assembly;and a second service valve which is disposed within said second serviceport of said second valve assembly and which is thereby fluidlyinterconnected with said first chamber of said second valve assembly,wherein said second fluid conduit extends between said second fluidinlet of said second valve assembly and said second fluid vessel.
 18. Asystem, as claimed in claim 17, wherein: said first fluid vesselcomprises an expandable/contractable vessel, wherein said second fluidvessel is at least substantially rigid, and wherein said first fluidvessel is disposed within said second fluid vessel.
 19. A system, asclaimed in claim 18, wherein: said second fluid vessel comprises arocket fuel storage vessel, wherein contraction of said first fluidvessel allows rocket fuel to be loaded within said second fluid vessel,and wherein expansion of said first fluid vessel is used to dischargerocket fuel from said second fluid vessel.
 20. A system, as claimed inclaim 19, wherein: said first rocket fuel storage vessel comprises asupply of hydrazine.
 21. A system, as claimed in claim 17, wherein: saidfirst and second barrier assemblies each comprise at least onepartition.
 22. A system, as claimed in claim 21, wherein: said at leastone partition of said first barrier assembly is integrally formed withsaid first valve body, and wherein said at least one partition of saidsecond barrier is integrally formed with said second valve body.
 23. Asystem, as claimed in claim 21, wherein: said at least one partition ofeach of said first and second barrier assemblies comprise separate firstand second partitions which are spaced from each other.
 24. A system, asclaimed in claim 17, wherein: said first and second barrier ruptureassemblies each comprise at least one initiator and at least oneprojectile.
 25. A system, as claimed in claim 17, wherein: said firstand second barrier rupture assemblies each comprise a first initiatorand a corresponding first projectile, as well as a second initiator anda corresponding second projectile.
 26. A system, as claimed in claim 17,wherein: said first service valve may be used to provide a first fluidto said first fluid vessel through said first valve assembly and priorto a rupturing of said first barrier assembly by directing said firstfluid into said second chamber of said first valve assembly, throughsaid first outlet, and through said first service valve, and therebywithout entering said first chamber of said first valve assembly; andsaid second service valve may be used to direct a second fluid out ofsaid second fluid vessel through said second valve assembly and prior toa rupturing of said second barrier assembly by directing said secondfluid through said second inlet of said second valve assembly, into saidfirst chamber of said second valve assembly, and through said secondservice valve, and thereby without entering said second chamber of saidsecond valve assembly.
 27. A system, as claimed in claim 17, wherein:said first service valve may be used to receive a first fluid from saidfirst fluid vessel through said first valve assembly and prior to arupturing of said first barrier assembly by a drawing of said firstfluid into said second chamber of said first valve assembly, throughsaid first outlet, and through said first service valve, and therebywithout entering said first chamber of said first valve assembly; andsaid second service valve may be used to direct a second fluid into saidsecond fluid vessel through said second valve assembly and prior to arupturing of said second barrier assembly by directing said second fluidthrough said second inlet, into said first chamber of said second valveassembly, and through said second service valve, and thereby withoutentering said second chamber of said second valve assembly.
 28. Asystem, as claimed in claim 17, further comprising: a first fluid supplysystem interconnected with said first inlet of said first valveassembly; a second fluid supply system interconnected with said firstservice valve of said first valve assembly; a rocket fuel tank; aplurality of rocket engine modules fluidly interconnected with saidrocket fuel tank; a third fluid conduit extending between said secondoutlet of said second valve assembly and said rocket fuel tank; a thirdsaid service port which extends within said second valve body and whichis fluidly interconnected with said second chamber of said second valveassembly; a third service valve which is disposed within said thirdservice port of said second valve assembly and which is thereby fluidlyinterconnected with said second chamber of said second valve assembly; athird fluid supply system fluidly interconnected with said third servicevalve; and a rocket fuel supply system fluidly interconnected with saidsecond service valve.
 29. A system, as claimed in claim 28, wherein:said first and second service valves may be used for a first unloadingoperation which is associated with said second fluid vessel, wherein forsaid first unloading operation a second fluid from said second fluidsupply is directed to said first fluid vessel through said first valveassembly, prior to a rupturing of said first barrier assembly, bydirecting said second fluid through said first service valve, thenthrough said second chamber of said first valve assembly, then throughsaid first outlet of said first valve assembly, and then through saidfirst fluid conduit to said first fluid vessel, while at the same time arocket fuel from said second fluid vessel is directed out of said secondfluid vessel through said second valve assembly, prior to a rupturing ofsaid second barrier assembly, by directing said rocket fuel through saidsecond inlet of said second valve assembly, then into said first chamberof said second valve assembly, and then through said second servicevalve; said first and second service valves may be used for a firstloading operation which is associated with said second fluid vessel,wherein for said first loading operation a first fluid from said firstfluid vessel is directed through said first valve assembly, prior to arupturing of said first barrier assembly, by drawing said first fluidout of said first fluid vessel and through said first fluid conduit,then through said first outlet of said first valve assembly, thenthrough said second chamber of said first valve assembly, and thenthrough said first service valve, while at the same time said rocketfuel is directed from said rocket fuel supply system into said secondfluid vessel through said second valve assembly, prior to a rupturing ofsaid second barrier assembly, by directing said rocket fuel from saidrocket fuel supply system through said second service valve, thenthrough said second inlet of said second valve assembly, then into saidfirst chamber of said second valve assembly, and then through saidsecond fluid conduit to said second fluid vessel; said third servicevalve may be used for a second loading operation which is associatedwith said rocket fuel tank, wherein for said second loading operation athird fluid from said third fluid supply system is directed to saidrocket fuel tank through said second valve assembly, prior to arupturing said second barrier assembly, by directing said third fluidthrough said third service valve, then into said second chamber of saidsecond valve assembly, then through said second outlet of said secondvalve assembly, and then through said third fluid conduit to said rocketfuel tank; and said third service valve may be used for a secondunloading operation which is associated with said rocket fuel tank,wherein for said second unloading operation said third fluid from saidrocket fuel tank is directed through said second valve assembly, priorto a rupturing said second barrier assembly, by directing said thirdfluid through said third fluid conduit, then through said second outletof said second valve assembly, then into said second chamber of saidsecond valve assembly, and then through said third service valve.
 30. Asystem, as claimed in claim 28, wherein: after actuation of said firstand second barrier rupture assemblies, a first fluid from said firstfluid supply system is directed through said first inlet, said first andsecond chambers, and said first outlet of said first valve assembly,then through said first fluid conduit and to said first fluid vesselwhich exerts a force on a rocket fuel within said second fluid vesseland which then displaces said rocket fuel from said second fluid vesselout through said second conduit, then through said second inlet, saidfirst and second chambers, and said first outlet of said second valveassembly, and then through said third fluid conduit to said rocket fueltank.
 31. A valve which comprises: a valve body; an inlet and an outletwhich extend within said valve body; first and second chambers which aredisposed within said valve body and which are fluidly interconnectedwith said inlet and outlet, respectively; a barrier assembly which isdisposed within said valve body and which isolates said first chamberfrom said second chamber; a barrier rupture assembly which isinterconnected with said valve body and which is directed toward saidbarrier assembly; and first and second service ports which extendthrough said valve body and which are fluidly interconnected with saidfirst and second chambers, respectively.
 32. A valve, as claimed inclaim 31, wherein: said barrier assembly comprises at least onepartition.
 33. A valve, as claimed in claim 32, wherein: said at leastone partition is integrally formed with said valve body.
 34. A valve, asclaimed in claim 32, wherein: said at least one partition comprisesseparate first and second partitions which are spaced from each other.35. A valve, as claimed in claim 31, wherein: said barrier ruptureassembly comprises at least one initiator and at least one projectile.36. A valve, as claimed in claim 31, wherein: said barrier ruptureassembly comprises a first initiator and a corresponding firstprojectile, as well as a second initiator and a corresponding secondprojectile.
 37. A valve, as claimed in claim 31, further comprising: apressure transducer interconnected with said valve body which fluidlyinterfaces with only one of said first and second chambers prior to arupturing of said barrier assembly by said barrier rupture assembly.